Gyroscope



Dec. 13, 1966 G. F. EAST 3,290,943

GYROSGOPE Original Filed Dec. 4, 1961 2 Sheets-Sheet l INVENTOR. GEO/96EE EAST E- E BY X//Lfl Dec. 13, 1966 G. F. EAST 3,290,948

GYROSCOPE Original Filed Dec. 4, 1961 2 Sheets-Sheet 2 VEN TOR 650/96548 T W Z/z M United States Patent 3,290,948 GYROSCOPE George F. East,Whittier, Calif., assignor to Clary Corporation, San Gabriel, Calif., acorporation of California Original application Dec. 4, 1961, Ser. No.156,839, now

Patent No. 3,142,184, dated July 28, 1964. Divided and this applicationAug. 9, 1963, Ser. No. 301,038

3 Claims. (Cl. 74-5) This is a division of application Serial No.156,839, filed December 4, 1961, now Patent No. 3,142,184.

This invention relates to gyroscopes and has particular reference touniversal or gimbal supporting means therefor.

In certain gyroscope applications, such as guided missiles, it is highlydesirable to reduce the weight and size of the gyroscope to a minimumwithout impairing its efficiency. This generally requires that the rotordiameter be as large as possible relative to the gyroscope casing toprovide the highest possible angular momentum, consistent with the speedof the rotor.

Heretofore, gyroscopes of the above type have generally been mounted ingimbal rings which surround the rotor and permit universal movement ofthe gyroscope case relative to the rotor so that the rotor may retainits initial attitude in space relative to the gyroscope case or base.Therefore, the diameter of the rotor heretofore has been generallylimited by the size of the surrounding gimbal rings.

Accordingly, it is a principal object of the present invention toprovide a universal or gimbal mounting for a gyroscope in which thediameter of the rotor is not restricted by the size of the universal orgimbal support therefor.

Another object is to provide a universal gimbal mounting for a gyroscopein which the mounting is located within the confines of a hollow rotor.

Another object is to reduce the overall weight and size of a gyroscopeunit.

A still further object is to provide a gyroscope and universal mountingwhich may be readily assembled or dismantled.

The manner in which the above and other objects of the invention areaccomplished will be readily under stood on reference to the followingspecification when read in conjunction with the accompanying drawings,wherein:

FIG. 1 is a longitudinal sectional view through a gyroscope embodying apreferred form of the present invention.

FIG. 2 is a sectional view through the rotor and gimbal means and istaken along the line 2-2 of FIG. 1.

FIG. 3 is a sectional view taken substantially along the line 33 of FIG.1.

FIG. 4 is a fragmentary view similar to FIG. 1 but illustrating thecaging device in uncaged condition.

FIG. 5 is a side view of part of the movable gimbal.

FIG. 6 is a plan View of a part of the stationary gimbal.

Referring to the drawings, the gyroscope comprises a cylindrical case 11preferably of aluminum or other nonmagnetic material, to the right-handend of which is secured an end cap 12. A removable cover 13 isthreadably attached to the opposite end of the case. The cover has acentral hub 14 and forms an annular propellant chamber or compartment1.5 to receive an annular gas generating propellant 16. The chamber isclosed by a removable bulkhead or wall 17, the latter being threadablyattached to the hub and hermetically sealed around its periphery by anO-ring 18 of rubber or the like fitted within a circumferentiallyextending groove formed in the bulkhead and engaging the inner surfaceof the cover.

The remainder of the interior of the case 11 forms a rotor compartment19 in which a hollow rotor, generally indicated at 20, is provided. Thelatter is formed of a rim 21 of relatively heavy metal, such as brass,and a hub 22 of relatively light metal, such as aluminum, which issuitably secured to the rim. A pair of diametrically opposed permanentmagnets 23 are suitably embedded in the rim for the purpose of actuatinga suitable magnetically responsive counting mechanism (not shown) whichis effective to sense the movement of the magnets through the casewhereby the speed of the rotor may be determined.

The rotor hub 22 is formed into a conical turbine head 24 having pockets25 therein adapted to receive streams of propellant gases from jets 26mounted in the bulkhead 17 and communicating the interior of thepropellant chamber with the rotor compartment. As seen particularly inFIG. 3, the jets are spaced around the bulkhead 1'7 and are directed atan angle to the turbine head .24 to cause the streams of propellantgases transmitted thereby to impinge on the pockets 25 and thus effectrotation of the rotor.

The rotor is rotatably mounted on a shaft 27 by ball bearings 28 and 29.The bearings are retained on the shaft by a pair of nuts 30 and 31,which are threaded in tandem on one end of the shaft and are formed tojointly comprise a labyrinth seal surrounding the bearing 28 whicheffectively prevents any products of combustion,

such as ashes and other solids, carried by the propelling gases fromentering the beaings.

The shaft 27 forms part of a gimbal means generally indicated at 128 andlocated within the hollow rotor. For

i this purpose, the shaft is formed at its right-hand end into abifurcated yoke constituting a first gimbal and comprising two spacedarms 32 and 33 which are pivotally supported by coaxially extendingshaft sections 34 and 35 of a center block 36 through ball bearings 37.The center block, constituting a second gimbal, is, in turn, pivotallysupported by coaxial shaft sections 38 and 40 pivotally mounted by ballbearings 41 mounted in spaced arms 42 and 43 forming the yoked end of apedestal 44, the latter being attached by screws, i.e., 45, to the endcap 12. The axes of the shaft sections 34 and 38 are mutuallyperpendicular to each other and to the axis of rotation of the rotor topermit universal positioning of the case relative to the rotor.

It will be noted that the rotor 20 is balanced about the intersection ofthe axes of shaft sections 34 and 38 and to effect minor adjustment ofsuch balance, a counterweight in the form of an annular ring 46 isadjustably threaded on the interior of the rim.

The caging mechanism comprises a piston 47 which is slideable in acylinder 48 formed in the hub 14 of the case cover 13. An annularbushing 50 is threadably mounted in the cover to guide the outer end ofthe piston and to limit outward movement thereof. The piston carries acaging pin 51 which extends through an opening in the hub 14. The pinhas a conical end 49 which is adapted to cage the gyroscope by engagingan axial opening 52 formed in the shaft 27, as shown in FIG. 1.

For the purpose of maintaining the gyroscope in caged condition, alocking plunger 53 is slideiably mounted in a guide hole extendingradially in the piston and communicating with the atmosphere through a.vent 54. The plunger is provided with a latching shoulder 55 which, whenthe piston is moved to its caging' position shown in FIG. 1 against theaction of a compression spring 56,

may be moved into latching engagement with a shoulder a ment by spacers57, thereby permitting ignition of all surfaces thereof so as tofacilitate rapid generation of propellant gases which are directed inthe form of streams onto the turbine head of the rotor by the jets 26.An electrically operable firing cap 58 is attached to the propellantring 16 and is controlled by wires 60 from a suitable source outside thecase. In lieu of the propellant ring 16, the propellant may be formed ofa plurality of separate pieces in which the surfaces thereof arepreferably out of contact with each other and with the walls of thepropellant compartment.

The case 11 is provided with exhaust slots 61 extending through the wallthereof to permit venting of spent propellant gases after they impingeon the turbine head. Prior to ignition of the propellant, such openingsare sealed by frangible covers 62 of aluminum foil or the like.

Upon ignition of the propellant ring, the propellant gases generatedthereby cause rotation of the rotor and are also transmitted through anopening 63 in the hub 14 to the cylinder 48. As the pressure of such gasbuilds up, the piston is forced slightly to the right to center theshaft 27 and thereby hold the gyroscope in proper caged condition. Atthe same time, the gases force the latching plunger 53 radially inwardlyof the piston 47 to remove the latching shoulder 55 from engagement withthe bushing 50. Concurrently, the buildup of pressure within the rotorcompartment causes rupturing of the covers 62 to permit venting of thespent gases.

After the rotor has been brought up to optimum speed and the propellantring has burnt out, the pressure of the exhaust gases lowers to a pointwhere the spring 56 becomes effective to force the pin 51 and piston 47to the left into their positions shown in FIG. 4, thereby uncaging thegyroscope.

Means are provided for indicating the attitude of the case relative tothe axis of the rotor during operation of the gyroscope. For thispurpose, two potentiometer pickoif devices, generally indicated at 65and 66, are mounted on the gimbal means to indicate the relativeposition of the case about two axes of movement.

The pickoff device 65, which is representative of both piclcoff devices,comprises a plate 166 of insulating material which is attached to theshaft section 35 of the center block 36. Such plate carries a flexiblewiping brush 67 which is in wiping engagement with an electricallyresistive layer on a second plate 68 of insulating material which issuitably attached to the yoke arm 33 of the rotor support shaft 27. Thesimilar brush 69 of the second pickoff device is carried by the shaftsection 38 of the center block and is in wiping engagement with aresistive layer on a plate 72 carried by the arm 42 of the pedestal 44.Flexible wires connected to the brushes and conductive layers of thepickoif devices are passed through longitudinally extending passages,i.e., 70, in the center block and a similar passage 71 in the pedestal44 to appropriate indicating and/or control devices not shown.

Although the invention has been described in detail and certain specificterms and languages have been used, it is to be understood that thepresent disclosure is illustrative rather than restrictive and thatchanges and modifications may be made without departing from the spiritor scope of the invention as set forth in the claims appended hereto.

Having thus described the invention, what is desired to be secured byUnited States Letters Patent is:

1. A gyroscope comprising a hollow rotor, a support rotatably supportingsaid rotor for movement about a spin axis, said Support having spacedarms extending within said rotor on Opposite sides of said spin axis, a

universal pivot member, bearings in said arms supporting said pivotmember between said arms for movement about a second axis intersectingsaid spin axis, said second taxis extending at right angles to said spinaxis, said pivot member having a passage extending therein coaxially ofone of said bearings, a support element having spaced arms on oppositesides of said spin axis, hearings in said last mentioned arms supportingsaid pivot member between said last mentioned arms for movement about athird axis intersecting said spin axis, said third axis extending atright angles to said second axis, said support element having a passageextending therein, means responsive to angular movement between saidsupport and said pivot member for indicating said angular movement, anda flexible conductor extending serially through said passages andoperatively connected to said last mentioned means for conveying saidindication.

2. A gyroscope comprising a hollow rotor, a support rotatably supportingsaid rotor for movement about a spin axis, said support having spacedarms extending within said rotor, a universal pivot member, hearings insaid arms supporting said pivot member for movement about a second axisintersecting said spin axis and the center of mass of said rotor, saidsecond axis extending perpendicular to said spin axis, said pivot memberhaving a passage extending therethrough coaxially of one of saidbearings, a support element having spaced arms, bearings in said lastmentioned arms supporting said pivot member for movement about a thirdaxis intersecting said spin axis and said center of mass, said thirdaxis extending perpendicular to said second axis, said support elementhaving a passage extending therethrough, means responsive to angularmovement between said support and said pivot member for indicating saidangular movement, and a flexible conductor extending serially throughsaid passages and operatively connected to said last mentioned means forconveying said indication.

3. A gyroscope comprising a hollow rotor, a support rotatably supportingsaid rotor for movement about a spin axis, said support having spacedarms extending within said rotor, a universal pivot member, hearings insaid arms supporting said pivot member for movement about a second axisintersecting said spin axis and the center of mass of said rotor, saidsecond axis extending perpendicular to said spin axis, said pivot memberhaving a passage therethrough coaxially of one of said bearings, asupport member having spaced arms, bearings in said last mentioned armssupporting said pivot member for movement about a third axisintersecting said spin axis and said center of mass, said third axisextending perpendicular to said second axis, said support element havinga second passage extending therein, electrical means responsive toangular movement between said support and said pivot member forindicating said angular movement, and flexible electrical conductorsextending serially through said passages and operatively connected tosaid last mentioned means for conveying said indication.

References Cited by the Examiner UNITED STATES PATENTS 2,592,643 4/1952Barnes 745.34- 2,911,832 11/1959 Thierman 74-5.6 X 2,981,061 4/1961Lilligren 745.7 X 3,078,728 2/1963 Schlesman 745,

FRED C. MATTERN, JR., Primary Examiner.

MILTON KAUFMAN, Examiner.

J, D, PUFFER, Assistant Examiner,

1. A GYROSCOPE COMPRISING A HOLLOW ROTOR, A SUPPORT ROTATABLY SUPPORTINGSAID ROTOR FOR MOVEMENT ABOUT A SPIN AXIS, SAID SUPPORT HAVING SPACEDARMS EXTENDING WITHIN SAID ROTOR ON OPPOSITE SIDES OF SAID SPIN AXIS, AUNIVERSAL PIVOT MEMBER, BEARINGS IN SAID ARMS SUPPORTING SAID PIVOTMEMBER BETWEEN SAID ARMS FOR MOVEMENT ABOUT A SECOND AXIS INTERSECTINGSAID SPIN AXIS, SAID SECOND AXIS EXTENDING AT RIGHT ANGLES TO SAID SPINAXIS, SAID PIVOT MEMBER HAVING A PASSAGE EXTENDING THEREIN COAXIALLY OFONE OF SAID BEARINGS, A SUPPORT ELEMENT HAVING SPACED ARMS ON OPPOSITESIDES OF SAID SPIN AXIS, BEARINGS IN SAID LAST MENTIONED ARMS SUPPORTINGSAID PIVOT MEMBER BETWEEN SAID LAST MENTIONED ARMS FOR MOVEMENT ABOUT ATHIRD AXIS INTERSECTING SAID SPIN AXIS, SAID THIRD AXIS EXTENDING ATRIGHT ANGLES TO SAID SECOND AXIS, SAID SUPPORT ELEMENT HAVING A PASSAGEEXTENDING THEREIN, MEANS RESPONSIVE TO ANGULAR MOVEMENT BETWEEN SAIDSUPPORT AND SAID PIVOT MEMBER FOR INDICATING SAID ANGULAR MOVEMENT, ANDA FLEXIBLE CONDUCTOR EXTENDING SERIALLY THROUGH SAID PASSAGES ANDOPERATIVELY CONNECTED TO SAID LAST MENTIONED MEANS FOR CONVEYING SAIDINDICATION.